Damage mitigating apparatus comprises in one embodiment a damage mitigating aerial vehicle that has sensors for detecting flight related characteristics and a communication unit for commanding activation of parachute deploying apparatus and of a lift generator deactivation unit following determination of a flight failure. In one embodiment, an aerial vehicle transmits a critical failure alarm signal to an unmanned aircraft traffic management system (UTM) following detection of the failure, and the UTM transmits a warning signal to neighboring aerial vehicles that are predicted to be in a vicinity of the descent path of the failed aerial vehicle to avoid collision with the failed aerial vehicle. The damage mitigating apparatus facilitates performance of a damage mitigating operation.

An emergency parachute system for rescue of persons or of manned or unmanned aerial vehicles includes a storage unit, which contains at least one cavity with an opening. The emergency parachute system further includes at least two parachutes, each of which contains a canopy, suspension lines, and a riser. The canopies of the at least two parachutes are folded separately and arranged in the cavity or cavities of the storage unit ejectably. The centers of the canopies are mutually interconnected by means of connection cords on the top side in order to stablize the system during flight.

An aircraft emergency parachute deployment system (AEPDS) is disclosed. The AEPDS includes a parachute assembly coupled with an aircraft, a ballistic rocket assembly coupled to a top portion of the parachute assembly by a lanyard, an actuator for initiating launch of the ballistic rocket; and a control module configured to receive aircraft orientation measurements and controlling launch of the rocket when the spatial orientation the aircraft is within a pre-selected range of values.

The disclosure provides an HAPR apparatus comprising an inflatable frame configured to generate canopy extension based on surrounding atmospheric pressure. The inflatable frame has a first collapse load limit less than the weight of the canopy at a first pressurized state less than 75 kPa and a second collapse load limit greater than the weight of the canopy at a second pressurized state of greater than 95 kPa. The internal pressure of the inflatable frame is typically about 101 kPa. The HAPR apparatus allows ascension with the canopy hanging under its own weight to reduce ascension time, then generates canopy extension prior to release in essentially a zero velocity, zero dynamic pressure condition.

The disclosure provides an HAPR apparatus comprising an inflatable frame configured to generate canopy extension based on surrounding atmospheric pressure. The inflatable frame has a first collapse load limit less than the weight of the canopy at a first pressurized state less than 75 kPa and a second collapse load limit greater than the weight of the canopy at a second pressurized state of greater than 95 kPa. The internal pressure of the inflatable frame is typically about 101 kPa. The HAPR apparatus allows ascension with the canopy hanging under its own weight to reduce ascension time, then generates canopy extension prior to release in essentially a zero velocity, zero dynamic pressure condition.

Provided are an ejection device with reduced weight without reducing an ejection speed of an ejected object and a flying object including the ejection device. An ejection device 100 includes a piston member 10, a cylinder 14 which accommodates the piston member 10 and is provided with a hole portion 13 for allowing the piston member 10 to project outward during operation, a push-up member 15 pushed up in one direction by the piston member 10, an ejected object 16 pushed up while being supported by the push-up member 15, and a gas generator 17 which moves the piston member 10 in the cylinder 14, and in the ejection device 100, the push-up member 15 has a support portion 20 disposed on a distal end side of the piston member 10 with a tip of the piston member 10 in a moving direction of the piston member 10 set as a reference.

Provided are an ejection device with reduced weight without reducing an ejection speed of an ejected object and a flying object including the ejection device. An ejection device 100 includes a piston member 10, a cylinder 14 which accommodates the piston member 10 and is provided with a hole portion 13 for allowing the piston member 10 to project outward during operation, a push-up member 15 pushed up in one direction by the piston member 10, an ejected object 16 pushed up while being supported by the push-up member 15, and a gas generator 17 which moves the piston member 10 in the cylinder 14, and in the ejection device 100, the push-up member 15 has a support portion 20 disposed on a distal end side of the piston member 10 with a tip of the piston member 10 in a moving direction of the piston member 10 set as a reference.

To provide a parachute device capable of quickly and reliably opening a parachute even when an airflow effect during flying or falling of a flight device cannot be immediately obtained. A parachute device (4) includes a parachute (400), a parachute accommodation section (40) configured to accommodate the parachute, at least one flying body (43) connected to the parachute, and an ejection section (41) configured to hold the flying body and to eject the flying body held, and the flying body includes a flying body main body section (44) engaged with the ejection section, and a gas generating device (45) disposed in an internal space (440) defined by the ejection section and the flying body main body section, and configured to generate gas.

To provide a parachute device capable of quickly and reliably opening a parachute even when an airflow effect during flying or falling of a flight device cannot be immediately obtained. A parachute device (4) includes a parachute (400), a parachute accommodation section (40) configured to accommodate the parachute, at least one flying body (43) connected to the parachute, and an ejection section (41) configured to hold the flying body and to eject the flying body held, and the flying body includes a flying body main body section (44) engaged with the ejection section, and a gas generating device (45) disposed in an internal space (440) defined by the ejection section and the flying body main body section, and configured to generate gas.

A variable-geometry vertical takeoff and landing (VTOL) aircraft system may transport passengers from a departure point to a destination via partially or fully autonomous flight operations. The VTOL aircraft system may operate in hover-based ascent/descent modes, level-flight cruising modes, and transitional modes between the two. Thrust may be provided by ducted propeller units articulable relative to the fuselage; by articulating the airfoil struts connecting the thrust sources to the fuselage the thrust sources may be manipulated for ascent/descent, transition, and cruising. in order to control ascent, descent, and cruise. More precise thrust control may be achieved by further articulation of the annular propeller ducts relative to the airfoil struts. The airfoil struts and propeller ducts may present a wing-shaped or variably segmented cross section to maximize achievable lift.